Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade
AbstractThe following paper deals with the development of an optimized non-axisymmetric endwall contour for reducing the total pressure loss and for homogenizing the outflow of a highly-loaded compressor cascade. In contrast to former studies using a NACA-65 K48 cascade airfoil this study starts with the design of a new high-performance airfoil which is based on the aerodynamic boundary conditions of the NACA-65 K48 cascade. This new airfoil is then used as a basis. Optimizations of the airfoil and of the endwall contour are performed using the German Aerospace Center (DLR) in-house tool AutoOpti and the RANS (Reynolds-averaged Navier-Stokes)-solver TRACE (Turbomachinery Research Aerodynamic Computational Environment). Three operating points at an inflow Mach number of 0.67 with different inflow angles are used to secure a wide operating range. The optimized endwall contour changes the secondary flow in such a way that the corner stall is reduced which, in turn, significantly reduces the total pressure loss. The endwall contour in the outflow region leads to a considerable homogenization of the outflow in the near wall region. Using non-axisymmetric endwall shaping demonstrates a valuable measure to further improve highly-efficient compressor blading on the vane level. View Full-Text
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Reutter, O.; Rozanski, M.; Hergt, A.; Nicke, E. Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade. Int. J. Turbomach. Propuls. Power 2017, 2, 1.
Reutter O, Rozanski M, Hergt A, Nicke E. Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade. International Journal of Turbomachinery, Propulsion and Power. 2017; 2(1):1.Chicago/Turabian Style
Reutter, Oliver; Rozanski, Magdalena; Hergt, Alexander; Nicke, Eberhard. 2017. "Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade." Int. J. Turbomach. Propuls. Power 2, no. 1: 1.
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